Question

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a) Calculate the modulus of a cross-ply HS-carbon/epoxy laminate. Longitudinal fibre modulus (En)-230 GPa; transverse fibre modulus (E122)-20 GPa; matrix modulus (En)-3 GPa; fibre volume fraction (V) : 60%. [5 marks] b)(1) Explain the difference in failure of a single fibre in air and a single fibre embedded [5 marks] in a matrix. (2) How can a test that involves the fracture of a single fibre embedded in a matrix provide information about the fibre-matrix interface? (1) What is Glare®? (2) Where is it used and (3) what are its main advantages over aluminium? Use diagrams whenever necessary. c) [5 marks] (1) When can composites based on discontinuous "short" fibres have similar properties to those of continuous fibre composites? (2) What would be the advantage of using such a short fibre composite over a continuous fibre composite? d) [5 marks] e) 1) Calculate the first ply failure (FPF) strain and last ply failure (LPF) strain of a symmetric [0/90]s glass/epoxy laminate loaded in tension. Fibre volume fraction (V) 50%, fibre modulus (E)-70 GPa, matrix modulus (En)-3 GPa, fibre strength (o) 2000 MPa, matrix strength (Om)60 MPa, stress concentration factor (SCF) 2. (2) Draw the schematic stress-strain curve of the laminate including the values at FPF and LPF for laminate stiffness and strength. Assume linear elastic behaviour and perfect adhesion. (3) Why is FPF such an important criteria in composite design? [5 marks]

Answer 1

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Longitudinal modulus of com posite is :E11392GPa Tran sversemodulusof com posite is: Em E2 EF22 E2 20 F2Ξ 1224 GPa Scanned with CamScanner ES